A gas turbine engine (10) includes a nacelle (24) defining a centerline axis (A) and an annular splitter (30) radially inward from the nacelle. A spinner (32) is radially inward of the nacelle forward of a compressor section (14). A fan blade (36) extends from a fan blade platform (34). A distance X is the axial distance from a first point to a second point, wherein the first point is defined on a leading edge of the annular splitter and the second point is defined on a leading edge of the fan blade where the fan blade meets the fan blade platform. A distance H is the radial distance from the first point to the second point. The relative position of the first point and the second point is governed by the ratio of for reducing foreign object debris (FOD) intake into the compressor section.


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    Titel :

    Nacelle and compressor inlet arrangements


    Beteiligte:

    Erscheinungsdatum :

    21.08.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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