Preliminary fan design for a functionally silent aircraft has been performed with noise reduction as the primary goal. For such an aircraft the fan design must, in addition to delivering low cruise fuel burn, enable low jet and fan source noise during take-off. This requires the fan to be operating at low pressure ratio and high efficiency during take-off and, for conditions where the relative tip Mach number onto the fan is supersonic, ensuring the primary shock structure is ingested into the blade passage. To meet these requirements, flyover and cruise flow coefficients are matched using a variable area nozzle at the same time as delivering low take-off FPR. This places the sideline operating point near the shoulder of the characteristic and fixes the top of climb and cruise fan pressure ratios. For a 4-engine, 250pax, 4000nm silent aircraft this approach leads to a top of climb FPR of 1.45 requiring a 39 % increase in nozzle area at take-off. A fan rotor has been designed for this cycle with 20 blades, low tip loading and a 350 m/s top of climb tip speed.


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    Titel :

    Preliminary fan design for a silent aircraft


    Beteiligte:
    Crichton, Daniel (Autor:in) / Xu, Liping (Autor:in) / Hall, Cesare A. (Autor:in)


    Erscheinungsdatum :

    2006


    Format / Umfang :

    10 Seiten, 34 Quellen



    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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    Crichton, Daniel | Online Contents | 2007


    Airframe Design for "Silent Aircraft"

    Hileman, James / Spakovszky, Zoltan / Drela, Mark et al. | AIAA | 2007


    Noise Reduction Assessments and Preliminary Design Implications for a Functionally-Silent Aircraft

    Manneville, Alexis / Pilczer, Deborah / Spakovszky, Zoltan | AIAA | 2004


    Engine Design Studies for a Silent Aircraft

    Hall, Cesare A. | Online Contents | 2007


    Challenges in the Silent Aircraft Engine Design

    de la Rosa Blanco, Elena / Hall, Cesare / Crichton, D. | AIAA | 2007