Propulsion assembly for an aircraft, comprising a fuselage (10) extending along a longitudinal axis (X) and enclosing an inner casing, at least one ducted engine (20) fixed to said fuselage (10) and comprising an air inlet portion (20a), said air inlet portion (20a) being at least partially disposed in said inner casing, at least one plenum (50), the air inlet part (20a) is arranged in the inner shell at the upstream of the air inlet part (20a) and is in fluid communication with the air inlet part (20a), the air inlet (30) is formed in the outer wall of the machine body (10), an inlet (30a) of the air inlet (30) is partially defined by the outer wall of the machine body (10), and the air inlet (30) is configured to suck in external air and deflect the external air to the pressurizing chamber (50).

    航空器的推进组件,包括沿纵轴线(X)延伸并封闭内壳的机身(10),至少一个固定到所述机身(10)并包括进气口部分(20a)的涵道发动机(20),所述进气口部分(20a)至少部分地设置在所述内壳中,至少一个增压室(50),设置在所述进气口部分(20a)上游的内壳中并与所述进气口部分(20a)流体连通,形成在所述机身(10)的外壁上的至少一个进气口(30),所述进气口(30)的入口(30a)部分地由所述机身(10)的外壁界定,所述进气口(30)被配置为吸入外部空气并将其偏向所述增压室(50)。


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    Title :

    Improved propulsion assembly with boundary layer suction


    Additional title:

    具有边界层吸入的改进型推进组件



    Publication date :

    2022-03-04


    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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