A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Passive boundary layer bleed system for nacelle inlet airflow control


    Beteiligte:
    ZYSMAN STEVEN H (Autor:in) / LORD WESLEY K (Autor:in) / MILLER ROBERT M (Autor:in) / ATASSI OLIVER V (Autor:in)

    Erscheinungsdatum :

    2017-05-09


    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



    Supersonic-inlet boundary-layer bleed flow

    Harloff, Gary J. / Smith, Gregory E. | AIAA | 1996


    Modeling Supersonic Inlet Boundary-Layer Bleed Roughness

    Paynter, G.C. | Online Contents | 1993


    On supersonic-inlet boundary-layer bleed flow

    Harloff, Gary / Smith, Gregory | AIAA | 1995


    Modeling supersonic inlet boundary-layer bleed roughness

    PAYNTER, GERALD C. / TREIBER, DAVID A. / KNEELING, W. D. | AIAA | 1993


    Modeling supersonic inlet boundary layer bleed roughness

    PAYNTER, GERALD / TREIBER, DAVID / KNEELING, W. | AIAA | 1992