A gas turbine engine 10 for an aircraft has hydraulic actuators, a fuel circuit 50 with a high and low 53 pressure pump and a fuel metering system. Wherein a hydraulic fluid line 60 is configured to convey hydraulic fluid to a hydraulic fluid circuit of the aircraft. The engine further includes a fuel-hydraulic fluid heat exchanger 63 which has a fuel side on the fuel circuit between the low- and high-pressure pumps. The heat exchanger transferring heat from the hydraulic fluid line to the fuel circuit. The engine may include a fuel-oil heat exchanger 51 to transfer heat from the oil to the fuel. The hydraulic fluid line may include a bypass loop 62 for bypassing the heat exchanger. The engine may include a gearbox 30(fig.1) receiving an input from a core shaft and outputs drive to a fan 23(fig.1) at a lower speed. Also disclosed is a gas turbine engine including a hydraulic fluid line and an air-hydraulic fluid heat exchanger 64(fig.4) configured to transfer heat from the hydraulic fluid line to an airflow 65(fig.4) produced by the engine e.g., a bypass duct airflow.


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    Titel :

    Gas turbine engine


    Beteiligte:
    ANDREA MINELLI (Autor:in)

    Erscheinungsdatum :

    09.08.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F15B SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL , Druckmittelbetriebene Systeme allgemein



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