The invention relates to a de-icing device for an air intake (2) of an aircraft turbojet engine nacelle extending along an X-axis in which an air stream flows from upstream to downstream, the air intake (2) having an inner cavity (20), extending annularly about the X-axis, which comprises an inner wall (21) facing the X-axis and an outer wall (22) which is opposite the inner wall (21), the walls (21, 22) being connected by a leading edge, the de-icing device comprising at least one injector (3) for injecting a stream of hot air (FAC) into the inner cavity (20), the injector (3) comprising a nozzle (30) extending along a nozzle axis (X2), the nozzle (30) being configured to inject a stream of hot air (FAC) having a dissymmetry along the nozzle axis (X2).

    本发明公开了一种用于飞行器涡轮喷射引擎的短舱的进气管(2)的除冰装置,喷射引擎短舱沿轴线X延伸,气流在短舱中从上游向下游流动,进气管(2)包括绕轴线X周向延伸的内腔,内腔包括朝向轴线X的内壁(21)以及与所述内壁(21)相对的外壁(22),所述内壁(21)和外壁(22)通过前缘连接,除冰装置包括至少一个用于将热气流(FAC)喷射到内腔(20)的喷射器(3),喷射器(3)包括沿喷嘴轴(X2)延伸的喷嘴(30),喷嘴(30)被配置为沿喷嘴轴(X2)喷射不对称的热气流(FAC)。


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    Title :

    DE-ICING DEVICE FOR AN AIR INTAKE OF AN AIRCRAFT TURBOJET ENGINE NACELLE


    Additional title:

    用于飞行器涡轮喷射引擎短舱进气管的除冰装置


    Contributors:

    Publication date :

    2021-10-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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