The invention discloses a turboprop engine power device for a single-engine double-wing aircraft, and belongs to the technical field of turboprop engine power devices. Comprising a body; the canopy is arranged at the upper end of the fuselage; the engine compartment used for providing thrust is located at the front end of the fuselage; the four-blade propeller is arranged at the front end of the engine compartment; and the empennage is arranged at the tail end of the fuselage. The problem that in the prior art, a turboprop engine is common in heat dissipation effect is solved, the ventilation cooling system is arranged and is an air cooling heat dissipation device, redundant heat of the engine is discharged out of the engine, the fan is driven by the engine to rotate, a driving component of the fan is omitted, installation is convenient and compact, the heat dissipation effect is good, and the cost is low. And the engine can work stably.

    本发明公开了一种用于单发双翼飞机的涡桨发动机动力装置,属于涡桨发动机动力装置技术领域。包括机身;其还包括有:座舱盖,其设置在机身的上端;发动机舱,用于提供推力的发动机舱位于所述机身的前端;四叶螺旋桨,其设置在发动机舱的前端;尾翼,其设置在机身的末端。本发明解决了现有技术中涡桨发动机散热效果一般的问题,通过设置通风冷却系统,该系统为风冷散热装置,将发动机多余的热量排出机外,通过发动机驱动风扇转动,省去了风扇的驱动部件,安装方便紧凑,散热效果好,使发动机能够稳定工作。


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    Titel :

    Turboprop engine power device for single-engine double-wing aircraft


    Weitere Titelangaben:

    一种用于单发双翼飞机的涡桨发动机动力装置


    Beteiligte:
    SUN FENGQIN (Autor:in) / ZHONG ZHIYONG (Autor:in) / TIAN YINQIAO (Autor:in) / TANG XUELIAN (Autor:in) / CUI ZHIHUA (Autor:in)

    Erscheinungsdatum :

    2023-03-07


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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