A study was made of an advanced technology airplane using supercritical aerodynamics. Cruise Mach number was 0.98 at 40,000 feet altitude with a payload of 60,000 pounds and a range of 3000 nautical miles. Separate-flow turbofans were examined parametrically to determine the effect of sea-level-static 8 at 40,000 feet altitude with a payload of 60,000 pounds and a range of 3000 nautical miles. Separate-flow turbofans were examined parametrically to determine the effect of sea-level-static design turbine-inlet-temperature and noise on takeoff gross weight (TOGW) assuming full-film turbine cooling. The optimum turbine inlet temperature was 2650 F. Two-stage-fan engines, with cruise fan pressure ratio of 2.25, achieved a noise goal of 103.5 EPNdB with todays noise technology while one-stage-fan engines, achieved a noise goal of 98 EPNdB. The take-off gross weight penalty to use the one-stage fan was 6.2 percent. (Author)


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    Titel :

    Optimization of Engines for a Commercial Mach 0.98 Transport Using Advanced Turbine Cooling Methods


    Beteiligte:
    G. A. Kraft (Autor:in) / J. B. Whitlow (Autor:in)

    Erscheinungsdatum :

    1972


    Format / Umfang :

    71 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch