A turboprop powered aircraft having a cowling or nacelle surrounding the engine, said cowling incorporates an air inlet and internal ducting to the engine wherein the inlet incorporated anti-icing ducts, said inlet shape has a closed oval or other non-circular shape that is not coaxial to the engine propeller drive shaft. Inlet anti-icing heating duct means are provided for channeling a portion of the engine's exhaust to the interior of the inlet rim. A further improvement in inlet efficiency can be achieved by reducing the thickness of the inlet cross-section, but this results in less space available for the hot exhaust connections.


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    Title :

    AIRCRAFT TURBOPROP ENGINE INLET COMPACT PROFILE CONFIGURATION


    Contributors:

    Publication date :

    2024-09-12


    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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