A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system 202 utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500°F. The system additionally includes a fuel system 206 having a deoxygenation unit 212 for deoxygenating fuel in the fuel system 206, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit 212. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system 202 and the fuel in the fuel system 206 for transferring heat from the oil in the first engine system 202 to the fuel in the fuel system 206.


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    Titel :

    熱管理システム


    Erscheinungsdatum :

    2018-06-13


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Japanisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / 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



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