A disclosed gas turbine engine includes a fan including a plurality of fan blades rotatable about an engine axis and core engine disposed within a core nacelle for driving the fan. A bypass passage is defined between the core nacelle and an outer or fan nacelle. A duct mounted within the core nacelle defines a bleed air flow path for directing bleed air from the core engine into the bypass passage. The bleed air duct includes a plurality of airfoils disposed at a defined chord angle for directing bleed airflow into the bypass passage to minimize disruption to bypass airflow.


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    Title :

    BLEED DUCT FOR LAMINAR FAN DUCT FLOW


    Contributors:

    Publication date :

    2015-10-01


    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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