Engine bleed air system (1) of an aircraft, comprising a heat exchanger (2) which comprises a rectangular core (3) with a rectangular outlet section (4), a cylindrical outlet duct (6), and a transition area (5) between the rectangular outlet section (4) of the rectangular core (3) and the cylindrical outlet duct (6), and at least a downstream system (7), further comprising flow deflecting means (8) located at least in the cylindrical outlet duct (6), such that the outlet flow (10) characteristics homogeneity are improved and a particular flow deflection and distribution of said outlet flow (10) is achieved, avoiding the damage of the at least one downstream system (7), and method for homogenizing the temperature of the outlet flow (10) of a heat exchanger outlet (2) in an engine bleed air system (1) of an aircraft.


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    Titel :

    HEAT EXCHANGER OUTLET DEFLECTOR


    Weitere Titelangaben:

    WÄRMETAUSCHERAUSLASSDEFLEKTOR
    DÉFLECTEUR DE SORTIE D'UN ÉCHANGEUR DE CHALEUR


    Beteiligte:

    Erscheinungsdatum :

    2017-09-20


    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



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