The invention relates to a turboprop (TP) comprising a propeller (2) comprising a blade extending in a direction (α), and which comprises a root (35), a leading edge (31), a trailing edge (32), and a wing tip (36), and an inner air stream channel (4), wherein said inner air stream channel (4) comprises an inlet (41) located at the root (35) of the blade (3) and an outlet (42) leading to the trailing edge (32) of the blade (3) and which is transversely directed in relation to the main elongation direction (α), such that an inner stream of air (51) flowing in the inner air stream channel (4) by entering via the inlet (41) adjacent to the root (35) of the blade (3) is discharged via the outlet (42) adjacent to the trailing edge (32) of the blade (3) by forming a stream of blown air (52) that moves away from the trailing edge (32) in a direction which is transverse to the main elongation direction (α) and which has a component in the direction of a skeleton line of the blade (3) at the trailing edge (32).


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    Title :

    Turboprop



    Publication date :

    2017-10-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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