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.


    Access

    Download


    Export, share and cite



    Title :

    Systems and Methods for Cooling Bleed Air from an Aircraft Engine


    Contributors:

    Publication date :

    2019-09-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke



    SYSTEMS AND METHODS FOR COOLING BLEED AIR FROM AN AIRCRAFT ENGINE

    CERRA DAVID F / TRETOW PAUL R | European Patent Office | 2024

    Free access

    Systems and methods for cooling bleed air from an aircraft engine

    CERRA DAVID F / TRETOW PAUL R | European Patent Office | 2021

    Free access

    Engine Bleed Air Systems for Aircraft

    SAE Technical Papers | 2004


    Engine Bleed Air Systems for Aircraft

    SAE Technical Papers | 2007


    Engine Bleed Air Systems for Aircraft

    SAE Technical Papers | 2020