A gas turbine for an aircraft includes: blades each including a blade body extending outward from a rotor rotating about an axis in a radial direction of the rotor and a fin protruding from an outer peripheral surface of a blade shroud formed on a distal end of the blade body; a casing installed to form gaps between the casing and the fins; and vanes each including a vane shroud formed such that at least a leading end portion of the vane shroud formed upstream in an axial direction is located outside with respect to an extended line of an inner peripheral surface of the casing in the radial direction.


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    Titel :

    Gas turbine for aircraft


    Beteiligte:
    FUJIMURA DAIGO (Autor:in) / WATANABE HIROSHI (Autor:in) / HANADA TADAYUKI (Autor:in) / HASE TAKAAKI (Autor:in)

    Erscheinungsdatum :

    2021-09-07


    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 / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    Britain's turbine aircraft

    Engineering Index Backfile | 1951


    Aircraft gas turbine

    Foster, G.H. | Engineering Index Backfile | 1949


    AIRCRAFT TURBINE ENGINE

    SERVANT REGIS EUGENE HENRI / DESOMBRE DIDIER GABRIEL BERTRAND / JACQUEMARD CHRISTOPHE PAUL | Europäisches Patentamt | 2022

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    Aircraft gas turbine engines

    Engineering Index Backfile | 1948


    INLET CONE FOR AN AIRCRAFT TURBINE ENGINE AND ASSOCIATED AIRCRAFT TURBINE ENGINE

    BATONNET BAPTISTE RENE ROGER / LOUIS ALBAN FRANCOIS | Europäisches Patentamt | 2022

    Freier Zugriff