The invention relates to a scoop (30) for an aircraft turbine engine (10), the scoop comprising a body (40) movable between at least two positions, the at least two positions comprising a first position in which the body is configured to trap a portion of a first airflow (28) flowing in a first direction, characterized in that the body is configured to trap a portion of the first airflow (28) flowing in a second direction. The main body can move to a second position, and a second position, the body is configured to trap a portion of a second air flow (28 ') flowing in a second direction, the second direction being opposite the first direction, and the body being mounted to be free to move between the at least two positions to automatically assume the first position when the first air flow flows and to automatically assume the second position when the second air flow flows. And automatically assumes the second position when the second airflow flows.

    本发明涉及一种用于飞行器涡轮发动机(10)的勺状部(30),该勺状部包括主体(40),主体能在至少两个位置之间移动,至少两个位置包括第一位置,在第一位置,主体被构造成捕集在第一方向上流动的第一空气流(28)的一部分,其特征在于,所述主体能移动到第二位置,在第二位置,主体被构造成捕集在第二方向上流动的第二空气流(28’)的一部分,第二方向与第一方向相反,并且所述主体被安装成在所述至少两个位置之间自由移动,以当第一空气流流动时自动地采用第一位置,并且当第二空气流流动时自动地采用第二位置。


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    Title :

    Spoon for aircraft turbine engine


    Additional title:

    用于飞行器涡轮发动机的勺状部



    Publication date :

    2023-08-15


    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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