In or for an aircraft turbine engine, the invention comprises a fitting comprising at least one blade, said blade being elongate and being adapted to be located such that it lies across the mouth of the engine inlet in use, such that, in use, the blade shears the air flowing towards it, such that the force of at least a portion of the air flowing Into the turbine is reduced, The invention also comprises a housing for a gas turbine engine, comprising a fitting of the invention and wherein the fitting is mounted at the, in use, front of the housing, the front of the housing having an inside periphery, and wherein the fitting is mounted within the inside periphery of the housing,


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    Title :

    Fitting for a gas turbine engine


    Contributors:

    Publication date :

    2016-08-31


    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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