A system for delivering a flow stream of a gas to a compressor. A shroud extends from an inlet to the compressor and defines a main inlet passage configured to direct the flow stream from the inlet to the compressor. A communication plenum is separated from the main inlet passage. A port system includes first and second port subsystems that each provide an opening between the main inlet passage and the communication plenum. The first port subsystem is disposed further from the compressor than the second port subsystem. The port system is configured so that a portion of the gas enters or exits the compressor through the second port subsystem, depending on operating conditions of the compressor.


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    Titel :

    Ported shroud system for turboprop inlets


    Beteiligte:
    BOULDIN BRUCE DAN (Autor:in) / RICE DEREK ANTHONY (Autor:in) / BARTON MICHAEL TODD (Autor:in) / MCCAGE RAYMOND (Autor:in) / WONG YATES (Autor:in) / SING KEVIN (Autor:in)

    Erscheinungsdatum :

    2021-09-21


    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 / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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