The invention relates to adaptable flow control for engine nacelles. An inlet flow distortion control system employs a plurality of flow control devices forming at least one array integrated into an internal surface of the inlet. The at least one array extends over an azimuthal range relative to a normal flow axis of the inlet and has a plurality of circumferential rows spaced at increasing distance from a highlight of the inlet. A control system is operably connected to the flow control devices and adapted to activate flow control devices in selected sub-arrays of the array responsive to a predetermined flight condition.

    本公开涉及用于引擎机舱的自适应流控制。一种入口流畸变控制系统采用形成集成在入口内表面中的至少一个阵列的多个流控制装置。至少一个阵列相对于入口的法向流动轴在方位角范围上延伸,并且具有与入口的突出部分以增加的距离间隔开的多个周向行。控制系统可操作地连接到流控制装置,并且适于响应于预定的飞行状况来激活阵列的所选子阵列中的流控制装置。


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    Titel :

    ADAPTABLE FLOW CONTROL FOR ENGINE NACELLES


    Weitere Titelangaben:

    用于引擎机舱的自适应流控制


    Beteiligte:
    RAFFERTY BRADLEY J (Autor:in) / DEFORE MATTHEW C (Autor:in) / GLEZER ARI (Autor:in) / VUKASINOVIC BOJAN (Autor:in) / NICHOLS DEREK A (Autor:in)

    Erscheinungsdatum :

    2021-11-19


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



    Adaptable flow control for engine nacelles

    RAFFERTY BRADLEY J / DEFORE MATTHEW C / GLEZER ARI et al. | Europäisches Patentamt | 2023

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