A parametric study was made of a group of separate-flow-turbofan engines for use in advanced technology airplanes designed for a cruise Mach number of 0.85 at 40,000 feet. The three-engined airplanes were sized to carry 200 passengers 3000 nautical miles. Supercritical aerodynamics were assumed. Film-cooled turbines were used and sea-level-static turbine-rotor-inlet temperature was always 2600 F. The optimum cycle depends on the noise goal assumed. Without a noise goal the best fan pressure ratio (FPR) is about 1.90. At noise goals of FAR 36, -10 EPNdb, and -20 EPNdb, the best FPR's are 1.85, 1.76, and 1.70, respectively, at cruise. The take-off FPR's are progressively less than the cruise value as the noise goal approaches -20 EPNdb. The penalties in take-off gross weight incurred were 8.5, 19, and 64 percent at goals of FAR 36, -10 EPNdb, and -20 EPNdb, respectively. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Optimization of Engines for a Commercial Mach 0.85 Transport Using Advanced Turbine Cooling Methods


    Contributors:
    G. A. Kraft (author)

    Publication date :

    1972


    Size :

    42 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English