A link part for a turbine engine which mounted between a fan cone and a fan disk supporting fan blades is provided. The link part includes an annular wall pierced by a plurality of orifices, each orifice for receiving a fastener member and terminated by a substantially perpendicular rim having an outer surface that provides an aerodynamic extension of the fan between an outer surface of the fan cone and an outer surface of a fan blade platform. The annular wall is made of a first material that is composite and is provided on an inner surface of the rim with a ring made of a second material that is different from the first and that is suitable for radially retaining the fan blade platform.


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    Titel :

    Axisymmetric part for an aviation turbine engine rotor


    Beteiligte:

    Erscheinungsdatum :

    2016-03-15


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64C AEROPLANES , Flugzeuge / F02K JET-PROPULSION PLANTS , Strahltriebwerke / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



    General Aviation Turbine Engine (GATE) Study

    C. F. Baerst / D. G. Furst | NTIS | 1979


    General aviation turbine engine /GATE/ concepts

    Lays, E. J. / Murray, D. L. | NTRS | 1979


    General aviation turbine engine /GATE/ concepts

    LAYS, E. / MURRAY, D. | AIAA | 1979


    General Aviation Turbine Engine (GATE) study

    Baerst, C. F. / Furst, D. G. | NTRS | 1979