The turboshaft engine for a rotorcraft includes a low pressure spool having a low pressure compressor and a low pressure turbine section, and a high pressure spool having a high pressure compressor and a high pressure turbine section. The spools are independently rotatable relative to one another. The low pressure compressor section includes a mixed flow rotor. A set of variable guide vanes (VGVs) are disposed upstream of each of the low pressure and high pressure compressors, the VGVs being configured to be independently operable relative to one another.


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    Titel :

    TURBOSHAFT GAS TURBINE ENGINE


    Beteiligte:
    MORGAN KEITH (Autor:in) / DUROCHER ERIC (Autor:in)

    Erscheinungsdatum :

    2020-02-13


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / 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 / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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