A turboprop includes a rotary propeller upstream from an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, the bypass having an outlet oriented substantially axially towards the downstream of the engine. The turboprop further includes a nacelle surrounding the engine and the air intake, wherein the air intake is secured to a housing of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle. The outlet is connected by a flexible link to an intake of an air circuit carried by the nacelle.


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    Title :

    Turboprop air intake


    Contributors:

    Publication date :

    2019-10-01


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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