The invention relates to a turbofan aircraft engine that comprises a primary duct including a combustion chamber; a first turbine disposed downstream of the combustion chamber; a compressor disposed upstream of the combustion chamber and coupled to the first turbine; and a second turbine disposed downstream of the first turbine and coupled to a fan for feeding a secondary duct of the turbofan aircraft engine. The bypass ratio of the inlet area of the secondary duct to the inlet area of the primary duct is at least 7 and the second turbine comprises at least two stages. For the first stage the mean radius r of a stator vane expressed in inch divided by the number of stator vanes is at least 0.18.


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    Titel :

    REDUCED NOISE TURBOFAN AIRCRAFT ENGINE


    Beteiligte:

    Erscheinungsdatum :

    2017-06-08


    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 / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02K JET-PROPULSION PLANTS , Strahltriebwerke



    Aircraft turbofan noise

    Groeneweg, J.F. / Rice, E.J. | Tema Archiv | 1982


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    GARDES PASCAL / MENOU FABIEN / GOUGEON PASCAL et al. | Europäisches Patentamt | 2021

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    CORIN ROBERT J / WHURR JOHN R | Europäisches Patentamt | 2024

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    SUPERSONIC AIRCRAFT TURBOFAN ENGINE

    CORIN ROBERT J / WHURR JOHN R | Europäisches Patentamt | 2020

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    Turbofan-engine noise suppression

    MARSH, A. | AIAA | 1966