The invention discloses a power system of a hybrid turboprop engine, the power system comprises a gas turbine engine, a driving motor, a parallel operation reduction gear mechanism main body, a propeller, blades, an auxiliary device and a stabilizing device. The parallel operation reduction gear mechanism body is mounted in the auxiliary device, and two groups of lubricating mechanisms are mounted in the auxiliary device, the lubricating mechanisms can automatically and continuously lubricate transmission positions at the two ends of the parallel operation reduction gear mechanism body, manual operation is reduced, and the working efficiency is effectively improved. The stabilizing device is installed on the periphery of the connecting shaft rod at the right end of the parallel operation speed reduction gear mechanism body, the stabilizing pieces at the upper end and the lower end are installed in the stabilizing device to stabilize the shaft rod and prevent the shaft rod from deviating during rotation, the outer sides of the stabilizing pieces are connected with the adjusting mechanism to adjust the supporting position, and the applicability is high and the stability is good.

    本发明公开了一种混合动力型涡桨发动机的动力系统,包括燃气涡轮发动机、驱动电机、并车减速齿轮机构主体、螺旋桨、浆叶、辅助装置和稳固装置,本发明通过将并车减速齿轮机构主体安装在辅助装置内,辅助装置内安装有两组润滑机构,润滑机构可实现自动的对并车减速齿轮机构主体两端传动位置的持续润滑,减少人工的操作,有效的提高了工作的效率;通过在并车减速齿轮机构主体右端连接轴杆周边安装有稳固装置,稳固装置内安装有上下两端稳固件,来实现对轴杆进行稳固,防止其在转动时发生偏移,稳固件外侧与调节机构相接,来实现支撑位置的调节,适用性强,稳定性好。


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    Titel :

    Power system of hybrid turboprop engine


    Weitere Titelangaben:

    一种混合动力型涡桨发动机的动力系统


    Beteiligte:
    LI MING (Autor:in) / ZHANG LIQIANG (Autor:in) / GAO HUA (Autor:in) / CHEN BO (Autor:in) / WANG SHIZHU (Autor:in)

    Erscheinungsdatum :

    2021-06-18


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F16H Getriebe , GEARING



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