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 subarrays of the array responsive to a predetermined flight condition.


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    Titel :

    Adaptable flow control for engine nacelles


    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 :

    03.01.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



    ADAPTABLE FLOW CONTROL FOR ENGINE NACELLES

    RAFFERTY BRADLEY J / DEFORE MATTHEW C / GLEZER ARI et al. | Europäisches Patentamt | 2021

    Freier Zugriff


    Application of Laminar Flow to AERO Engine Nacelles

    A. J. Mullender / A. L. Bergin / D. I. A. Poll | NTIS | 1991



    Hybrid Laminar Flow Control Applied to Advanced Turbofan Engine Nacelles

    Collier, F. S. / Arcara, P. C. / Wie, Y. S. | SAE Technical Papers | 1992