The invention relates to a cooling system and method for an electric aircraft propulsion system. The cooling system comprises: an energy source (1); one or more heat exchangers (2) for cooling a coolant and connected to the energy source (1) by means of a coolant circuit (3, 4); one or more air channels (6) inside which one or more heat exchangers (2) are placed, where said coolant circuit (3, 4) comprises a bypass portion (5) that: recirculates coolant to the energy source (1); or circulating coolant from the energy source (1) to the one or more heat exchangers (2). The cooling system and method allow the cooling capacity of the system to be enhanced during a takeoff phase, in particular during the start of the takeoff phase.

    本发明涉及用于电动飞行器推进系统的冷却系统和方法。冷却系统包括:能量源(1);一个或更多个热交换器(2),所述一个或更多个热交换器(2)用于使冷却剂冷却并且通过冷却剂回路(3、4)连接至所述能量源(1);一个或更多个空气通道(6),一个或更多个空气通道内部放置有一个或更多个热交换器(2),其中,所述冷却剂回路(3、4)包括旁路部分(5),该旁路部分:将冷却剂再循环至能量源(1);或者将冷却剂从能量源(1)循环至一个或更多个热交换器(2)。该冷却系统和方法允许增强系统在起飞阶段期间、特别是在起飞阶段开始期间的冷却能力。


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    Title :

    Cooling system and method for electric aircraft propulsion system


    Additional title:

    用于电动飞行器推进系统的冷却系统和方法


    Contributors:

    Publication date :

    2023-01-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

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




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