一种用于飞行器的辅助功率单元,具有:发动机核心;压缩机,具有与发动机核心的入口流体连通的出口;涡轮机区段,与发动机核心的出口流体连通;以及过量空气管道,具有与压缩机的出口流体连通的第一端和与涡轮机区段的涡轮机的入口流体连通的第二端。过量空气管道限定在压缩机的出口和涡轮机区段之间的与发动机核心分离的流动路径。辅助功率单元可包括与发动机核心驱动接合的发电机,以便向飞行器提供电功率。还公开了向飞行器提供压缩空气和电功率的方法。

    An auxiliary power unit (10) for an aircraft, having an engine core (12), a compressor (18) having an outlet (180) in fluid communication with the engine core inlet (120), a turbine section (20) in fluid communication with the engine core outlet (120), and an excess air duct (82) having a first end in fluid communication with the compressor outlet (180) and a second end in fluid communication with a turbine inlet (240) of the turbine section (20). The excess air duct (82) defines a flow path between the compressor outlet (180) and the turbine section (20) separate from the engine core (12). The auxiliary power unit may include a generator (14) in driving engagement with the engine core (12) to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.


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    Title :

    具有过量空气回收的辅助功率单元


    Publication date :

    2021-04-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

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