Intakes of gas turbine engines are subject to cross winds and high incidence cross flows which can affect the stability of air to the propulsive fan. A gas turbine engine having a rotational axis, an intake and a compressed gas source; the intake includes a lining having a facing which defines an inlet surface and an array of holes; the array of holes comprises at least a first set of holes and a second set of holes, the holes of the first set of holes are angled ± relative to a radial line and the holes of the second set of holes are angled ² relative to the radial line; the angles ± and ² are different. An active flow control arrangement comprising a compressed gas supply pipe, a valve arrangement, a controller, a compressed gas distribution pipe may be provided. Compressed gas may be provided to prevent the formation of separation of a main gas flow through the intake and prevent or remove ice accretion.


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    Title :

    Intake liner for a gas turbine engine


    Additional title:

    Einlasskanaleinlage für einen Gasturbinenmotor
    Revêtement de conduit d'admission pour moteur à turbine à gaz


    Contributors:

    Publication date :

    2017-05-03


    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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