The invention discloses a power system of a double-engine parallel turboprop engine. The power system comprises a protective cover, an open groove, a parallel operation reduction gearbox, a propeller, a right inclined strut clutch, a left driven straight gear, a right driven straight gear, a parallel operation driven bevel gear, a flange end face and cooling buffer mechanisms. The cooling buffer mechanisms are arranged at the upper ends of a first gas turbine engine and a second gas turbine engine, and the first gas turbine engine and the second gas turbine engine are connected in series through a first fixing ring and a second fixing ring, so that the first gas turbine engine and the second gas turbine engine are fixed stably and are not prone to shaking due to impact of external force. Meanwhile heat transfer on the upper ends of the first gas turbine engine and the second gas turbine engine is accelerated through a circulating cooling mechanism, and the advantage that the first gas turbine engine and the second gas turbine engine can be stably fixed and cooled is achieved.

    本发明公开了一种双发并车型涡桨发动机的动力系统,包括保护罩、开槽、并车减速齿轮箱、螺旋桨、右斜撑离合器、左从动直齿轮、右从动直齿轮、并车从动斜齿轮、法兰端面和冷却缓冲机构。本发明通过在第一燃气涡轮发动机和第二燃气涡轮发动机上端设置了冷却缓冲机构,通过第一固定环和第二固定环将第一燃气涡轮发动机和第二燃气涡轮发动机相互串接在一起,使第一燃气涡轮发动机和第二燃气涡轮发动机固定稳固,不易受外力冲击摇晃,同时通过循环冷却机构加快第一燃气涡轮发动机和第二燃气涡轮发动机上端热传递,达到了能够使第一燃气涡轮发动机和第二燃气涡轮发动机平稳固定和降温的优点。


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    Titel :

    Power system of double-engine parallel turboprop engine


    Weitere Titelangaben:

    一种双发并车型涡桨发动机的动力系统


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

    Erscheinungsdatum :

    2021-06-11


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F16F SPRINGS , Federn



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