An aircraft engine system configured with a high pressure stage turbocharger assembly and a supplemental stage turbocharger assembly disposed in series with respect to said high pressure stage turbocharger, wherein the supplemental stage turbocharger assembly provides a compressor unit of the high pressure stage turbocharger with substantially constant critical altitude pressure input.


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    Title :

    Multistage turbocharging system for providing constant original critical altitude pressure input to high pressure stage turbocharger


    Contributors:
    FASS YEHUDA (author) / FELDMAN JACOB (author)

    Publication date :

    2021-03-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02B INTERNAL-COMBUSTION PISTON ENGINES , Brennkraftmaschinen mit innerer Verbrennung mit Verdrängerwirkung / F02D CONTROLLING COMBUSTION ENGINES , Steuern oder Regeln von Brennkraftmaschinen / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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