The invention relates to a propeller blade (34) radially extending between a blade foot (38) and a blade head (36), and comprising a leading edge (40) and a trailing edge (42), in addition to an active surface and a passive surface. According to the invention, along the leading edge (30), the angle (a) between the radial direction and a tangent to the trailing edge passes through a local maximum zmax arranged between 60 and 80 % of the height of the blade (34). Furthermore, the passive surface of the blade (34) comprises an indentation (54) extending axially from the leading edge (40) up to the trailing edge, and arranged at the top of the blade (34) between the local maximum zmax and the blade head (34).


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    Titel :

    Propeller blade for turbomachine


    Beteiligte:

    Erscheinungsdatum :

    12.08.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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