A gas turbine engine (10) includes a core engine (16) including a compressor section (20) communicating air to a combustor section (22) where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section (24). The turbine section (24) is coupled to drive the compressor section (20). A propulsor (18) aft of the core engine (16) is driven by the turbine section (24). An exhaust duct (42) routes exhaust gases around the propulsor (18). The exhaust duct (42) includes an inlet (46) forward of the propulsor (18), an outlet (40) aft of the turbine section (24) and a passageway between the inlet and the outlet.


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    Title :

    EXHAUST DUCT FOR TURBINE FORWARD OF FAN


    Additional title:

    ABGASLEITUNG FÜR EINE TURBINE VOR EINEM FAN
    CONDUIT D'ÉCHAPPEMENT POUR TURBINE SITUÉE EN AVANT D'UNE SOUFFLANTE


    Contributors:

    Publication date :

    2020-10-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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