The present disclosure includes: a core engine including a core casing that covers a low-pressure rotary structure and a high-pressure rotary structure and includes a passage of air flowing through the low-pressure rotary structure and the high-pressure rotary structure; a fan located in front of the core engine; an inner cowl that serves as an inner peripheral surface of a bypass passage that extends through the fan and bypasses the core engine; an accessory gear box that extracts power from the low-pressure rotary structure or the high-pressure rotary structure and supplies the extracted power to various accessories; an auxiliary compressor that is attached to the accessory gear box, is driven by driving power of the accessory gear box, and increases pressure of compressed air extracted from the core engine; and a compressed air pipe that extends through an inside of a strut connecting the core engine and an airframe and supplies to the airframe the compressed air that has been increased in pressure by the auxiliary compressor. The accessory gear box and the auxiliary compressor are located in an inner space between the core casing and the inner cowl.


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    Titel :

    AIRCRAFT GAS TURBINE ENGINE


    Weitere Titelangaben:

    FLUGGASTURBINENTRIEBWERK
    MOTEUR À TURBINES À GAZ D'AÉRONEF


    Beteiligte:
    TAKAMI HIROAKI (Autor:in) / SEKOGUCHI NAOYA (Autor:in) / ISHIDA KATSUHIKO (Autor:in) / UMEZAKI KENTA (Autor:in) / SAKAMOTO HIROSHI (Autor:in) / GOI TATSUHIKO (Autor:in)

    Erscheinungsdatum :

    10.07.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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