A gas turbine engine includes a fan received within a fan case, the fan delivers bypass air into a bypass duct between an inner radial portion of the fan case and an outer radial surface of an inner core housing. The fan also delivers air into the inner core housing. A compressor section, a combustor and a turbine are within the inner core housing. A bifurcation extends radially to connect the inner core housing to the fan case. The bifurcation has a forward opening defining an air scoop. The air scoop separates air into a first airflow chamber connected downstream to a precooler. The precooler also has a connection to receive compressed air from the compressor section. The air in the bypass duct is delivered to the precooler for cooling the compressed air in the precooler. The air scoop also defines a second airflow chamber for delivering cooling air to components within the inner core housing. An aircraft supply system is also disclosed.


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    Title :

    Bifurcation Air Scoop for Gas Turbine Engine


    Contributors:

    Publication date :

    2025-05-08


    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



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