A gas turbine engine 200, 200', 200" for mounting to an airframe of an aircraft comprises an engine core 210; a fan 214 located upstream of the engine core 210; a bifurcation 204 spanning a bypass duct 202 defined between the engine core 210 and a nacelle 221 surrounding the gas turbine engine 200, 200', 200", the bifurcation 204 comprising aerodynamically shaped fairings 206 defining an interior space 208 therebetween; and a cabin blower system 100 arranged in the interior space 208 of the bifurcation 204.


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    Title :

    GAS TURBINE ENGINE WITH CABIN BLOWER SYSTEM


    Additional title:

    GASTURBINENMOTOR MIT KABINENGEBLÄSESYSTEM
    TURBINE À GAZ COMPRENANT UN SYSTÈME DE VENTILATEUR DE CABINE


    Contributors:

    Publication date :

    2024-06-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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