Systems and methods for cooling bleed air from an aircraft engine are described. An example system includes a housing to bifurcate airflow exiting a fan of an engine fan system, a pre-cooler assembly disposed within the housing to remove heat from the bleed air, and an inlet duct within the housing to direct the airflow to the pre-cooler assembly. The example system also includes at least one diverter duct within the housing and coupled to the inlet duct to divert the airflow around the pre-cooler assembly. The at least one diverter duct includes an exit directing the airflow into a fan duct of the engine fan system. The example system also includes at least one valve to control an amount of airflow through the inlet duct and an amount of airflow through the at least one diverter duct.


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    Titel :

    Systems and Methods for Cooling Bleed Air from an Aircraft Engine


    Beteiligte:
    CERRA DAVID F (Autor:in) / TRETOW PAUL R (Autor:in)

    Erscheinungsdatum :

    12.09.2019


    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 / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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