A gas turbine engine has a nose cone, a fan for delivering air into a bypass duct as bypass flow, and into a core engine to be delivered to a compressor. The nose cone includes a vent to receive air and deliver the air across a heat exchanger, which receives a fluid to be cooled. The air from the vents is delivered to an outlet downstream of the heat exchanger, such that a majority of the air being delivered to the outlet becomes part of the bypass flow.


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    Titel :

    Engine with nose cone heat exchanger and radially outer discharge


    Beteiligte:

    Erscheinungsdatum :

    2019-02-26


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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