The invention belongs to the technical field of aero-engine architecture design for more-electric aircrafts, and particularly relates to an aero-engine architecture for more-electric aircrafts, which can be used for extracting power from a high-pressure shaft and a low-pressure shaft on the basis of maintaining a main engine structure of an aero-engine, and also can be used for extracting power from a high-pressure shaft and a low-pressure shaft. According to the invention, the engine-attached receiver and the flight-attached receiver are designed in an integrated manner, the engine-attached and flight-attached integrated receiver is adopted, and the generator and the starter corresponding to the engine-attached and flight-attached integrated receiver are designed in an integrated manner, and the integrated starter/generator is adopted, so that power extraction from a high-pressure shaft can be promoted, and the electric power requirement of a more-electric aircraft can be well met.

    本申请属于多电飞机用航空发动机架构设计技术领域,具体涉及一种多电飞机用航空发动机架构,能够在维持航空发动机主机结构基础上,设计除了自高压轴提取功率外,同时能够自低压轴提取功率,此外,对发附机匣、飞附机匣进行了集成设计,采用发附飞附一体化机匣,以及对用发附飞附一体化机匣对应的发电机与起动机进行了集成设计,采用一体化起动/发电机,可促进自高压轴上提取功率,能够很好的满足多电飞机的电功率需求。


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    Titel :

    Aero-engine framework for more-electric aircraft


    Weitere Titelangaben:

    一种多电飞机用航空发动机架构


    Beteiligte:
    ZHANG DONGMEI (Autor:in) / MENG QINGMING (Autor:in) / YU XUEMING (Autor:in)

    Erscheinungsdatum :

    2023-06-30


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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