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.


    Access

    Download


    Export, share and cite



    Title :

    TURBOSHAFT GAS TURBINE ENGINE


    Contributors:

    Publication date :

    2020-02-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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



    TURBOSHAFT GAS TURBINE ENGINE

    MORGAN KEITH / DUROCHER ERIC | European Patent Office | 2020

    Free access

    TURBOSHAFT GAS TURBINE ENGINE

    MORGAN KEITH / DUROCHER ERIC | European Patent Office | 2023

    Free access

    Turboshaft gas turbine engine

    MORGAN KEITH / DUROCHER ERIC | European Patent Office | 2022

    Free access