An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, in flow series, an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight. A method of designing a nacelle for a gas turbine engine includes the steps of: defining such an initial geometry for the nacelle; pivoting, at each of one or more positions on the highlight and in the plane of the respective longitudinal section, the front portion of the section of intake lip lying in the respective longitudinal section about the highlight; and obtaining an altered geometry for the nacelle by adjusting surfaces of the intake neighbouring the pivoted front portion to smoothly blend the surfaces of the pivoted front portion to unadjusted surfaces of the intake further removed from the pivoted front portion.


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    Titel :

    Gas turbine engine nacelle


    Weitere Titelangaben:

    Gasturbinen-Triebwerksgondel
    Nacelle de turboréacteur


    Beteiligte:

    Erscheinungsdatum :

    10.10.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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