Provided is a method of operating a gas turbine engine. The engine includes a combustor having a plurality of fuel spray nozzles and a fuel system arranged to provide fuel to the combustor. The system includes: fuel pump; fuel distributing valve downstream of the pump arranged to distribute fuel to the plurality of nozzles and bias fuel flow to the nozzles such that a first subset of the plurality of nozzles receives more fuel than a second subset of the plurality of nozzles; and fuel-oil heat exchanger. The method includes providing a fuel to the combustor and transferring heat from oil to the fuel in the fuel-oil heat exchanger before the fuel enters the combustor so as to lower a viscosity of the fuel to 0.58 mm2/s or lower on entry to the combustor at cruise conditions. Also provided is a gas turbine engine for an aircraft.


    Access

    Download


    Export, share and cite



    Title :

    AIRCRAFT FUEL SYSTEM


    Contributors:

    Publication date :

    2024-06-27


    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



    Aircraft fuel system and aircraft

    HASHIMOTO JUNICHIRO / KOMODA USHIO | European Patent Office | 2016

    Free access

    AIRCRAFT FUEL SYSTEM

    WOOD JOHN | European Patent Office | 2018

    Free access

    AIRCRAFT FUEL SYSTEM

    MORGAN ANGUS / SLACK CHRISTOPHER | European Patent Office | 2017

    Free access

    AIRCRAFT FUEL SYSTEM

    BURNELL STEPHEN / LEIGH TIM | European Patent Office | 2018

    Free access

    Aircraft fuel system

    DYLAN JAMES / JUSTINE MCCARTHY / ANGUS MORGAN et al. | European Patent Office | 2017

    Free access