A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A combustor section is arranged axially between the compressor section and the turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. A heat exchanger is secured to the oil tank and arranged in the core compartment.


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    Titel :

    GAS TURBINE ENGINE OIL TANK


    Weitere Titelangaben:

    GASTURBINENMOTORÖLTANK
    RÉSERVOIR D'HUILE DE MOTEUR À TURBINE À GAZ


    Beteiligte:
    SUCIU GABRIEL L (Autor:in) / SNAPE NATHAN (Autor:in) / DYE CHRISTOPHER M (Autor:in)

    Erscheinungsdatum :

    2016-12-21


    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 / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F01M Schmierung von Kraft- und Arbeitsmaschinen oder Kraftmaschinen allgemein , LUBRICATING OF MACHINES OR ENGINES IN GENERAL



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