According to embodiments of the present invention, provided is an auxiliary power unit for an aircraft capable of transmitting rotational power with a relatively low reduction ratio and reducing the overall weight and size of the auxiliary power unit. The auxiliary power unit for an aircraft comprises: a compression unit which compresses air flowing in from the outside to generate high-pressure gas; a combustion unit which mixes fuel with the high-pressure gas received from the compression unit; a turbine unit disposed on a flow path of the gas introduced from the combustion unit; a shaft unit which shares a central axis with the turbine unit and rotates in conjunction with the rotation of the turbine unit; a power generation unit which receives power from the shaft unit and produces electrical energy; and a power transmission unit disposed between the power generation unit and the shaft unit, and transmitting power to the power generation unit.

    본 발명의 실시예들에 따르면, 외부로부터 유입되는 공기를 압축시켜 고압 가스를 발생시키는 압축부와, 압축부로부터 전달받은 고압 가스와 연료를 혼합시키는 연소부와, 연소부로부터 유입되는 가스의 유동 경로 상에 배치되는 터빈부와, 터빈부와 중심축을 공유하고, 터빈부의 회전과 연동되어 회전되는 샤프트부와, 샤프트부로부터 동력을 전달받아 전기에너지를 생산하는 발전부 및 발전부와 샤프트부 사이에 배치되며, 발전부로 동력을 전달하는 동력전달부를 포함하고, 발전부는 복수 개가 구비되어 동력전달부에 연결되는 것을 특징으로 하는 항공기용 보조 동력 장치를 제공한다.


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    Titel :

    Auxiliary power unit for aircraft


    Weitere Titelangaben:

    항공기용 보조 동력 장치


    Beteiligte:
    KIM JAE YEOP (Autor:in) / CHOI WOO YOUNG (Autor:in) / NAM KI YONG (Autor:in)

    Erscheinungsdatum :

    2021-10-08


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Koreanisch


    Klassifikation :

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



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