A gas turbine engine includes a spool, a turbine coupled with the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool and a gear assembly coupled between the propulsor and the spool such that rotation of the spool results in rotation of the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge such that the chord forms a stagger angle α with the axis. The stagger angle α is less than 62° at all positions along the span, with said hub being at 0% of the span and the tip being at 100% of the span.


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    Titel :

    FAN STAGGER ANGLE FOR GEARED GAS TURBINE ENGINE


    Weitere Titelangaben:

    LÜFTERSTAFFELUNGSWINKEL FÜR GETRIEBEGASTURBINENMOTOR
    ANGLE DE DÉCALAGE DE SOUFFLANTE POUR TURBINE À GAZ AYANT UNE BOÎTE DE VITESSE


    Beteiligte:
    GALLAGHER EDWARD J (Autor:in) / MONZON BYRON R (Autor:in) / LIU LING (Autor:in) / LI LINDA S (Autor:in) / WHITLOW DARRYL (Autor:in)

    Erscheinungsdatum :

    22.08.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / 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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