A turbo engine for an aircraft includes a gas turbine engine having a fuel system to provide fuel to a combustion section. The fuel system includes a variable displacement pump driven by an accessory gearbox that is powered by a shaft of the gas turbine engine. The variable displacement pump has an inlet side and an outlet side. The variable displacement pump includes an actuator configured to adjust a discharge flow rate of the variable displacement pump. The fuel system also includes a fuel metering valve configured to receive pressurized fuel from the variable displacement pump and control a flow rate of the pressurized fuel to the combustion section. The fuel system further includes a bypass valve fluidly coupling the outlet side and the inlet side of the variable displacement pump to direct an excess portion of the pressurized fuel at the outlet side back to the inlet side.


    Access

    Download


    Export, share and cite



    Title :

    FUEL SYSTEMS FOR AIRCRAFT ENGINES



    Publication date :

    2025-02-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



    Fuel injection for aircraft engines

    Wiegand, F.J. / Meador, D.W. | Engineering Index Backfile | 1944


    Aircraft engines with a fuel cell

    WICKERSHAM ANDREW / HART RICHARD | European Patent Office | 2023

    Free access

    AIRCRAFT WITH ELECTRIC AND FUEL ENGINES

    DU XING | European Patent Office | 2018

    Free access


    AIRCRAFT WITH ELECTRIC AND FUEL ENGINES

    DU XING | European Patent Office | 2019

    Free access