The invention provides an electric engine, an electric propulsion device and an aircraft, and relates to the technical field of aircrafts. The electric engine comprises a power motor which comprises a motor rear cover, and the motor rear cover is provided with a liquid inlet flow channel and a liquid supply flow channel; the liquid pump comprises a pump body and a pump rotor, the pump body is fixedly connected with the motor rear cover, a pump cavity of the liquid pump is formed between the pump body and the motor rear cover, the pump body forms part of the cavity wall of the pump cavity, and the pump cavity is communicated with the outlet end of the liquid inlet flow channel and the inlet end of the liquid supply flow channel; the pump rotor is arranged in the pump cavity and used for enabling cooling liquid in the liquid inlet flow channel to flow into the liquid supply flow channel through the pump cavity. Thus, the weight of the electric engine can be reduced, and the weight of the electric engine can be reduced.

    本申请提供一种电动发动机、电推进装置及飞行器,涉及飞行器技术领域。电动发动机包括:动力电机,其包括电机后盖,电机后盖具有入液流道和供液流道;液泵,包括泵体和泵转子,泵体与电机后盖固定连接,泵体与电机后盖之间具有液泵的泵腔,泵体形成泵腔的部分腔壁,泵腔连通入液流道的出口端和供液流道的进口端;泵转子设置在泵腔内,泵转子用于使入液流道内的冷却液经泵腔流向供液流道内。这样,可以减小电动发动机的重量,实现电动发动机的轻量化。


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    Title :

    Electric engine, electric propulsion device and aircraft


    Additional title:

    电动发动机、电推进装置及飞行器


    Contributors:
    XUE SONGBAI (author) / LI QING (author) / GONG ZHENG (author) / YI LIJIE (author) / SONG JIANBO (author)

    Publication date :

    2025-01-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS / H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES



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